WO2023026014A1 - Inverseur a grilles mobiles pour ensemble propulsif d'aeronef, comprenant un systeme pour limiter le flambage d'un actionneur de l'inverseur - Google Patents
Inverseur a grilles mobiles pour ensemble propulsif d'aeronef, comprenant un systeme pour limiter le flambage d'un actionneur de l'inverseur Download PDFInfo
- Publication number
- WO2023026014A1 WO2023026014A1 PCT/FR2022/051607 FR2022051607W WO2023026014A1 WO 2023026014 A1 WO2023026014 A1 WO 2023026014A1 FR 2022051607 W FR2022051607 W FR 2022051607W WO 2023026014 A1 WO2023026014 A1 WO 2023026014A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- grids
- actuator
- buckling
- reverser
- fixed
- Prior art date
Links
- 230000000670 limiting effect Effects 0.000 title claims abstract description 29
- 238000013519 translation Methods 0.000 claims description 2
- 230000002441 reversible effect Effects 0.000 description 6
- 238000013461 design Methods 0.000 description 5
- 230000033001 locomotion Effects 0.000 description 5
- 238000006073 displacement reaction Methods 0.000 description 4
- 238000009434 installation Methods 0.000 description 3
- 239000003831 antifriction material Substances 0.000 description 2
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000036961 partial effect Effects 0.000 description 1
- 230000002829 reductive effect Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 210000003462 vein Anatomy 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/64—Reversing fan flow
- F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
- F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
Definitions
- Reverser with moving grids for an aircraft propulsion system comprising a system for limiting the buckling of an actuator of the reverser
- the invention relates to the field of nacelles and thrust reversers for aircraft propulsion systems, and, more particularly, to nacelles equipped with reversers with mobile grids.
- Thrust reversers are devices for deflecting forward the flow of air passing through the propulsion unit, so as to shorten landing distances, and to limit the stress on the brakes on the landing gear.
- Grid inverters currently used in the aeronautical sector comprise a front frame forming with the grids a fixed part of the inverter, intended to be connected to a turbomachine casing.
- the mobility of the grids makes it possible to reduce the length of the nacelle, and, consequently, to reduce its mass as well as the drag that it generates.
- the invention firstly relates to a thrust reverser for an aircraft propulsion system, the reverser having a longitudinal central axis and comprising a fixed structure and a mobile system, the mobile system comprising at least one reverser cowl and at least one set of deflection gates comprising a plurality of deflection gates, the inverter also comprising an actuator equipped with a fixed part and a movable part with respect to the fixed part, so as to be able to move the system mobile in translation with respect to the fixed structure of the reverser along the longitudinal central axis, between an advanced position of direct thrust and a rearward position of reverse thrust.
- the mobile system also comprises an inter-grid structure for limiting buckling of the actuator, the inter-grid structure being interposed between two directly consecutive deflection grids and forming a channel through which the actuator passes, the channel being bounded by a cylindrical inner surface extending circumferentially along at least a portion of a first closed director curve of the cylindrical inner surface.
- the cylindrical inner surface then preferably extends circumferentially all along the first closed guide curve, or else is circumferentially interrupted by extending along only part of the first closed guide curve.
- the fixed part of the actuator passes through the channel and comprises an output end of the movable part, this output end being equipped with an outer ring for limiting buckling of the actuator, the ring having an outer surface cylindrical extending circumferentially along at least a portion of a second closed guide curve of the cylindrical outer surface.
- the cylindrical outer surface then preferably extends circumferentially all along the second closed guide curve, or else is interrupted circumferentially by extending along only part of the second closed guide curve.
- the first and second closed guide curves are, in view along the central axis longitudinal, of the same shapes and concentric being spaced from each other by the same spacing all along them.
- the two shapes could be different and/or the spacing could be non-constant, for example by providing that the first and second directing curves are not concentric, without departing from the scope of the invention.
- the invention preferably provides at least one of the following optional technical characteristics, taken individually or in combination.
- said at least one set of grids also comprises a rear structure for supporting the grids on which is fixed a rear end of the plurality of deflection grids, as well as a front structure for supporting the grids on which is fixed an end front of the plurality of deflection grids, and the inter-grid structure for limiting buckling comprises a front end and a rear end fixed respectively to the front support structure and to the rear support structure.
- the first and second closed guide curves have a circular shape. Nevertheless, other shapes can be envisaged, such as, for example, more ovalized shapes. These shapes are generally retained so as to be identical or substantially identical to the general shape of the fixed part of the actuator, provided with its possible external equipment.
- the cylindrical interior surface of the channel is circumferentially interrupted by extending along only a part of the first closed directing curve, so as to define several angular sectors of cylindrical interior surface, preferably two spaced angular sectors from each other, the inter-grid structure for limiting buckling being preferably made using two axial beams respectively defining the two angular sectors.
- each of these sectors extends for example over an amplitude greater than 100°.
- the inter-grid structure for limiting buckling is further functionalized so as to include an outer surface forming an axial sliding track for the mobile system. This makes it possible to reduce the friction forces, and to facilitate the displacement of the mobile system of the reverser between its two positions.
- the outer buckling limiting ring is made in one piece, split, or sectorized. When it is split or sectored, its installation and replacement on the fixed part of the actuator are thereby facilitated.
- the outer buckling limiting ring is made of an anti-friction material.
- the actuator is a hydraulic or electric jack.
- the invention also relates to a propulsion assembly for an aircraft, comprising a turbine engine and a nacelle equipped with a thrust reverser as described above.
- FIG. 1 is a diagrammatic half-view in longitudinal section of a propulsion assembly, comprising a thrust reverser shown in direct thrust configuration;
- FIG. 2 is a diagrammatic half-view in longitudinal section of the propulsion assembly shown in FIG. 1, with the reverser shown in reverse thrust configuration;
- FIG. 3 is an exploded perspective view of part of the nacelle of the propulsion assembly shown in the preceding figures, showing in particular the elements of the thrust reverser;
- FIG. 4 is an axial view of the rear support structures of the grids shown in the previous figure
- FIG. 5 is a partial perspective view, in more detail, of part of the inverter shown in the preceding figures;
- FIG. 6 is a diagrammatic half-view in longitudinal section of a rear part of the propulsion assembly shown in FIG. 1, in more detail, and still with the reverser in direct thrust configuration;
- FIG. 7 is a diagrammatic half-view in longitudinal section of a rear part of the propulsion assembly shown in FIG. 2, in more detail, and still with the reverser in reverse thrust configuration;
- FIG. 8 is a cross-sectional view taken along line VI II-VII I of Figure 6;
- FIG. 9 is a cross-sectional view similar to that of Figure 8, according to another preferred embodiment of the invention.
- FIG. 10 is a cross-sectional view similar to that of Figure 8, according to yet another preferred embodiment of the invention. Detailed Description of Embodiments
- FIG. 1 There is shown in Figures 1 and 2 an aircraft propulsion assembly 1, having a central longitudinal axis Al.
- front and rear are defined in relation to a general direction SI of gas flow through the propulsion assembly 1, along the axis Al when the latter generates thrust. These terms “front” and “rear” could respectively be substituted by the terms “upstream” and “downstream”, with the same meaning.
- the propulsion assembly 1 comprises a turbine engine 2, a nacelle 3 as well as a mast (not shown), intended to connect the propulsion assembly 1 to a wing (not shown) of the aircraft.
- the turbomachine 2 is in this example a turbofan and two-spool engine comprising, from front to rear, a fan 5, a low-pressure compressor 6, a high-pressure compressor 7, a combustion chamber 8, a high pressure turbine 9 and a low pressure turbine 10. Compressors 6 and 7, combustion chamber 8 and turbines 9 and 10 form a gas generator.
- the turbojet engine 2 has a fan casing 11 connected to the gas generator by structural arms 12.
- the nacelle 3 comprises a front section forming an air inlet 13, a middle section which comprises two fan cowls 14 enveloping the fan casing 11, and a rear section 15.
- an air flow 20 enters the propulsion assembly 1 through the air inlet 13, crosses the fan 5 and then divides into a primary flow 20A and a secondary flow 20B.
- the primary stream 20A flows in a primary stream 21A for gas circulation passing through the gas generator.
- the secondary stream 20B flows in a secondary stream 21B surrounding the gas generator.
- the secondary stream 21B is delimited radially inwards by a fixed internal fairing which envelops the gas generator.
- the fixed inner fairing comprises a first section 17 belonging to the middle section 14, and a second section 18 extending rearward from the first section 17, so as to form part of the rear section 15.
- the nacelle 3 comprises a thrust reverser 30 comprising on the one hand a fixed structure 31 integral with the fan casing 11, and on the other hand a system 29 movable with respect to the fixed structure 31.
- the movable system 29 of the reverser 30 comprises at least one set 32' of deflection grids 32, the aforementioned movable reverser cowls 33, shutters 34 and rods 35.
- the thrust reverser 30 is also centered on the axis Al, while like turbomachine 2.
- FIG. 2 shows the same reverser 30 in a reverse thrust configuration.
- the mobile inverter cowls 33 and the entire mobile system 29 are in an open position, or retracted position, in which the cowls 33 are longitudinally distant from the fixed structure 31 so as to define an opening radial of the secondary vein 21B.
- Grids 32 extend through this radial opening.
- the shutter flaps 34 are deployed radially in the secondary stream 21B so as to to direct the secondary flow 20B towards the grids 32, which make it possible to direct the flow thus redirected towards the front of the propulsion assembly 1, with the aim of generating a counter-thrust.
- the grids 32 and the movable cowls 33 of the movable system 29 are represented in a so-called retracted thrust reversal position.
- the fixed structure 31 is equipped with elements for guiding the grids 32 during their movement between the advanced and retracted positions, these elements comprising axial rails 40.
- these elements are two rails 40 secured to an upper part of the ring, and two other rails 40 integral with a lower part of this same ring.
- the rails 40 are fixed to the fixed structure 31 by their rear end, while their front end is fixed to another casing (not shown in FIG. 3).
- the rails 40 thus perform a function of guiding the grids 32 during their axial displacement, but also, in thrust reversal configuration, a function of absorbing aerodynamic forces, mainly radial and tangential.
- FIG. 3 schematically represents the grids 32, which follow one another in the circumferential direction 43. Here, they are grouped into two lateral sets each comprising several grids 32, these sets being called sets of deflection grids 32'.
- each grid 32 is therefore intended to be fixed on its associated rear structure 45, by conventional fixing means.
- each set of grids 32' also comprises a front structure 45' for supporting the grids, on which is fixed a front end of each of the deflection grids 32 of the set 32'.
- These front structures 45' are also called “front grid frames”, and they each extend circumferentially all along their associated side assembly 32', according to an identical or similar angular sector. The front end of each grid 32 is therefore intended to be fixed to its associated front structure 45', by conventional fixing means.
- the fixed structure 31 comprises members (not shown) forming radial and/or tangential and/or axial stops for the grids 32 of the assemblies 32'.
- the set of grids 32' comprises axial inter-grid structures 47, 47' arranged between the grids 32, along the circumferential direction 43 of the nacelle and of its reverser 30.
- These axial inter-grid structures 47, 47' are extend over the entire length or substantially the entire axial length of the assembly 32', and are therefore arranged between the grids 32, in the direction 43. With their radially outer surface 49, these axial structures 47, 47' form tracks sliding axial for the mobile system 29.
- it can be several kinds of structures, including elements 47 ensuring the function of mechanical junction between the grids 32, and intergrid structures for limiting buckling 47 ', specific to the present invention.
- a single inter-grid buckling limitation structure 47' is visible in FIG.
- the fixed part 54 of the jack 52 opens towards the front of the front end of the inter-grid structure for buckling limitation 47', while the mobile part 56 of the jack 52 opens towards the rear of the rear end of the inter-grid structure 47', as can also be seen in FIGS. 6 and 7 which will be described below.
- FIG. 6 shows the mobile system 29 of the reverser 30 in the advanced direct thrust position, in which the jack rod 56 is completely retracted into the jack cylinder 54, and the deflection grids 32, inoperative, covered by the covers fan 14.
- FIG. 7 shows the mobile system 29 in the rearward thrust reversal position, in which the actuator rod 56 is fully extended rearward, and the deflection grids 32 rearwardly moved back to be able to generate reverse thrust function.
- the output end 66 of the fixed part of the jack 52 is equipped with an outer ring 70 for limiting the buckling of the jack.
- the ring 70 arranged around the jack cylinder, has a cylindrical outer surface 62' extending circumferentially all along a second closed guide curve 64', here of circular shape and also centered on the axis A2.
- the cylindrical outer surface 62' of the intergrid structure 47' remains uninterrupted along the circumferential direction 43' of this structure 47', in relation to the axis A2.
- the cylindrical outer surface 62' therefore continuously follows the second closed guide curve 64' in the form of a circle, being defined by a generatrix parallel to the axis A2 which follows this same curve 64'.
- the first and second closed guide curves 64, 64' are preferably concentric and of the same shape. , the first being of larger size than the second so as to define a constant spacing 72 all along the latter in the direction 43'.
- the outer buckling limiting ring 70 can be made in one piece, that is to say in one piece, or else preferably be split or divided into sectors to facilitate its installation and its replacement around the fixed jack cylinder. In the case where this ring 70 is divided into sectors, it may for example be two half-shells attached around the jack cylinder.
- the ring is preferably made of a conventional antifriction material, known to those skilled in the art.
- an antifriction coating can be provided on ring 70 to form outer surface 64', without departing from the scope of the invention.
- the ring 70 can advantageously be replaced around the jack cylinder.
- the ring 70 moves axially relative to the channel 60 in motion.
- the output end 66 and the ring 70 which surrounds it are housed in the channel 60, close to a front end of the inter-grid structure 47 ' mobile.
- FIG. 6 shows another functionality of the rear structure 45 of the set of grids 32', which consists in producing the axial connection with the reverser cowl 33, in its closed flight position.
- the rear end of the structure 45 comprises an axial connecting member 76 in the form of an annular groove open radially outwards, cooperating with a complementary axial connecting member 78 provided on a front end of the reverser cowl 33.
- This member 78 preferably takes the form of a radial inward projection, housed in the groove 76 for obtaining the axial coupling in the closed position of the cover 33. When the latter is opened towards its open position maintenance, the projection 78 is extracted from the groove 76.
- the two curves 64, 64' remain circular, but the cylindrical inner surface 62 of the channel is no longer continuous. It is interrupted circumferentially by extending along only part of the first closed directing curve 64, so as to define several angular sectors of cylindrical inner surface 62a.
- the inter-grid structure for limiting buckling 47' is preferably made using two axial beams 47'a, 47'a respectively defining the two angular sectors 62a, 62a. Each beam extends the full length of the set of grids 32', being fixed at its ends to the front and rear support structures to which the front and rear ends of the grids 32 are also fixed.
- the surface interruptions 80 corresponding to empty portions between the two beams 47'a of the inter-grid structure 47', preferably extend over a small angular amplitude.
- Each angular sector of cylindrical inner surface 62a can, like all of its associated beam 47'a, extend over an amplitude greater than 100°, and for example close to 180° as shown in FIG. 9.
- the cylindrical outer surface 62' of the ring 70 by providing surface interruptions spacing angular sectors of cylindrical outer surface.
- the two closed directing curves 64, 64' are no longer in the shape of a circle, but for example slightly oval on one side so as to take account of the general shape of the part. fixed 54 of the cylinder, provided with its external equipment such as an oil return pipe 82 and its fitting 84 for holding the cylinder of the cylinder.
- the shape of the channel 60 and of the ring 70 can be adapted according to the general outer shape of the fixed part 54 of the cylinder 52, always while maintaining a constant radial spacing 72 in the unstressed buckling state.
- thrust reverser 30 can alternatively have a “C” or “O” architecture.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202280062755.7A CN117940660A (zh) | 2021-08-25 | 2022-08-24 | 用于飞行器推进单元的具有可移动叶栅叶片的反推力装置,包括用于限制反推力装置的致动器的屈曲的系统 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FRFR2108893 | 2021-08-25 | ||
FR2108893A FR3126452A1 (fr) | 2021-08-25 | 2021-08-25 | Inverseur à grilles mobiles pour ensemble propulsif d’aéronef, comprenant un système pour limiter le flambage d’un actionneur de l’inverseur |
Publications (1)
Publication Number | Publication Date |
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WO2023026014A1 true WO2023026014A1 (fr) | 2023-03-02 |
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PCT/FR2022/051607 WO2023026014A1 (fr) | 2021-08-25 | 2022-08-24 | Inverseur a grilles mobiles pour ensemble propulsif d'aeronef, comprenant un systeme pour limiter le flambage d'un actionneur de l'inverseur |
Country Status (3)
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CN (1) | CN117940660A (fr) |
FR (1) | FR3126452A1 (fr) |
WO (1) | WO2023026014A1 (fr) |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2132380A1 (fr) * | 1971-03-31 | 1972-11-17 | Short Brothers & Harland Ltd | |
EP1239139A1 (fr) * | 2001-03-08 | 2002-09-11 | Hurel-Hispano Le Havre | Système d'actionnement du capotage mobile d'un inverseur de poussée dans un turboréacteur |
FR2981989A1 (fr) | 2011-10-31 | 2013-05-03 | Aircelle Sa | Inverseur de poussee a grilles mobiles et capot mobile monobloc |
FR2999239A1 (fr) | 2012-12-12 | 2014-06-13 | Aircelle Sa | Inverseur de poussee de nacelle et nacelle equipee d'au moins un inverseur |
FR3002785A1 (fr) | 2013-03-01 | 2014-09-05 | Aircelle Sa | Grilles translatantes et fixes avec un t/r o-duct. |
WO2015028755A1 (fr) * | 2013-08-30 | 2015-03-05 | Aircelle | Nacelle à dispositif d'inversion de poussée à grilles mobiles maintenues |
FR3073572A1 (fr) | 2017-11-16 | 2019-05-17 | Safran Nacelles | Inverseur de poussee a grilles mobiles pour ensemble propulsif d’aeronef et procedes de montage et demontage s’y rapportant |
US10605197B2 (en) * | 2014-12-02 | 2020-03-31 | United Technologies Corporation | Gas turbine engine and thrust reverser assembly therefore |
WO2021044096A1 (fr) * | 2019-09-05 | 2021-03-11 | Safran Nacelles | Inverseur de poussée comprenant un unique vérin de commande de capot mobile |
-
2021
- 2021-08-25 FR FR2108893A patent/FR3126452A1/fr active Pending
-
2022
- 2022-08-24 WO PCT/FR2022/051607 patent/WO2023026014A1/fr active Application Filing
- 2022-08-24 CN CN202280062755.7A patent/CN117940660A/zh active Pending
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2132380A1 (fr) * | 1971-03-31 | 1972-11-17 | Short Brothers & Harland Ltd | |
EP1239139A1 (fr) * | 2001-03-08 | 2002-09-11 | Hurel-Hispano Le Havre | Système d'actionnement du capotage mobile d'un inverseur de poussée dans un turboréacteur |
FR2981989A1 (fr) | 2011-10-31 | 2013-05-03 | Aircelle Sa | Inverseur de poussee a grilles mobiles et capot mobile monobloc |
FR2999239A1 (fr) | 2012-12-12 | 2014-06-13 | Aircelle Sa | Inverseur de poussee de nacelle et nacelle equipee d'au moins un inverseur |
FR3002785A1 (fr) | 2013-03-01 | 2014-09-05 | Aircelle Sa | Grilles translatantes et fixes avec un t/r o-duct. |
WO2015028755A1 (fr) * | 2013-08-30 | 2015-03-05 | Aircelle | Nacelle à dispositif d'inversion de poussée à grilles mobiles maintenues |
US10605197B2 (en) * | 2014-12-02 | 2020-03-31 | United Technologies Corporation | Gas turbine engine and thrust reverser assembly therefore |
FR3073572A1 (fr) | 2017-11-16 | 2019-05-17 | Safran Nacelles | Inverseur de poussee a grilles mobiles pour ensemble propulsif d’aeronef et procedes de montage et demontage s’y rapportant |
WO2021044096A1 (fr) * | 2019-09-05 | 2021-03-11 | Safran Nacelles | Inverseur de poussée comprenant un unique vérin de commande de capot mobile |
Also Published As
Publication number | Publication date |
---|---|
FR3126452A1 (fr) | 2023-03-03 |
CN117940660A (zh) | 2024-04-26 |
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